Supersonic wind-tunnel flutter tests of two rectangular wings

dc.contributor.author	P. R. Guyett	en_US
dc.date.accessioned	2014-10-21T15:54:25Z
dc.date.available	2014-10-21T15:54:25Z
dc.date.issued	1956	en_US
dc.identifier.other	ARC/R&M-3080	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3650
dc.description.abstract	Two rectangular wings of aspect ratio 4 were flutter tested in a supersonic wind tunnel at Mach numbers 1.6 and 2.0 using a technique in which a structural stiffness was varied to give flutter at the Mach number. The results are in reasonable agreement with calculations using theoretical three-dimensional derivatives and arbitrary wing modes, though in general the calculated critical stiffnesses are rather higher than the test values. It is shown theoretically that structural damping has an important effect upon the stiffness required to avoid flutter, and may in some circumstances be destabilising.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Supersonic wind-tunnel flutter tests of two rectangular wings	en_US